Rocket fuel pump and the like



w. D. 'I 'EAGUE, JR

ROCKET FUEL PUMP AND THE LIKE Feb. 1, 1955 3 Sheets-Sheet 1 Filed. April 27. 1948 mw fi O Ali m y o mm l m g N9 n m mm. m u c w. l m T Q on 0Q 02 8 8 Wm m o 0 Mg om I mM l on w m mz v: N0 3 A an o o ww 2 2 W m: o o: 2. 8 Q. N\ 4 no l 8 in 2 Q. R m m AIM #2 m o 9 NN mm F m 3 y Zz/HLTEH 27. 759505 JR.

Feb. 1, 1955 w. D. TEAGUE, JR 2,700,935

ROCKET FUEL PUMP AND THE LIKE Filed April 27, 1948 3 Sheets-Sheet 2 IN VEN TOR.

H/f/L TER ZZTEHEUE JR.

Feb. 1, 1955 W. D. TEAGUE, JR

ROCKET FUEL PUMP AND THE LIKE 3 Sheets-Sheet. 3

Filed April 27. 1948 INVENTOR. [L /7L TEE D. TEF/EUE JR. BY M 14 w I? TTOR/VE Y United States Patent RGCKETFUEL PUMP. THE LIKE Walter D. Teague,- Jr.,-Al1iine, N. 1., assignor to Bendix altviation *Corporation, Te'terb'oro, N. J., a corporation 'otmelaware Application April 27, E1948, 'Serlal No. 23,581

3 "Claims. '(Cl. 103-4) The invention T'hereof relates to power, or turbine, means and toffuel ,pumps and other devices which may be drivenfbythepower means, asin an installation on a jet propelled vehicle, where a turbine wheel is impelled bythejjet. j j

In a fjet propelleddevice, an auxiliary source of {power may be required for pumping fuel, generating electricity or other purpose. Such power-may be obtained from a turbine which utilizes the energy of the high velocity exhaust .gasesas its driving means. I

In most jet-propelled or reaction engines, whether of the so-called turbo-jet, ram jet, or pure rocket type, after -the gases, which {make up the ,jet, :leave the ,jet noizleqthey no longer do any useful work. All of the propulsion effort is appliedin the nozzle and combustion chambers or the engine. v n

"Thus, aturbine'rnay befpla'ced the jet, behind the nozzle, Without affecting the jpropulsive effort of the jet in any "manner. The only net loss of such device resides inthe drag of "the iturbine blades, which creates a 'foree opposite in direction to thepropulsive force of ilr'etjet. Another characteristic of suChjets istheir very great velocity which, in most cases is considerably in excess of the speed of sound in-the jet gas medium.

'Fherefore, the most eflicient blade form will be one which supplies 'the required torque "with aslittle drag as possible. Unlike a conventional turbine, the "amount of jet 'gases flowing through the turbine is of no importance, since *the flow is present in any case, whether used in'driving the turbineofnot.

Since it is well-known that the aerodynamic reaction of a fluid passing over an airfoil produces lift and drag forces that are effective on the surfaces on the airfoil, and further "since there is an optimum angle of attack at which a given airfoil will develop a maximum lift force and a minimum drag'when placed ina fluid having a particular "velocity, the instant invention proposes a turbine blade designed and constructed to have thecharacteristics "of an airfoil and to mount said :blade on the tuib'i'ne wheel in atiposition to provide an optimum angle of attack of the blade relative to the jet. Dueto this design"and-construction, the lift forces developed by the bladeswill produce the required torque to rotate theturbine wheel and the drag induced bythe blades will be held t'oea minimum.

An; object 'of the invention is to provide ajturbine with the above-mentioned desirable characteristics and also, =to.,provide a blade which. exhibits good resistance to high centrifugal stresses.

:Another object is to provide a turbine, in which each blade has a supersonic airfoil section, such that, within its ability to effectively withstand the working stresses of itstrated load, it approaches the character of an infinitely thin flat plate having "an angle of incidence relative to the wheel axis to provide an angle of attack at which the Wheel is actuated at a given torque, with substantially-minimum reaction against the jet, and hence minimum drag on the vehicle.

Another object, for various advantages, is to provide atufbineofithe minimum drag aforesaid whichis adapted for combination with one or more features, such as a one-piece rotor element including a 'body and blades;

short compared to the diameterof the ,jet; blades adapted toextend only partially into the jet at one side of the latter; a disc-like "body and blades substantially wider than the axial thickness of the disc; "and blades which "ice convergingly taper outwardly as to outer-end substantially chisel edges.

Another object is to provide a rotatable unit which comprises adriving wheel, driven rotors disposed one at each side of "the wheel, and journal means outside each driven rotor from the wheel constituting the orily journal'means of the unit to provide wide bearing-support.

Another objectris to provide azpumpiincluding alrotor having-a (hollow hub or kshaft constituting a lpuinp ii'nlet, bearing means :for the shaft, and means 'providing for the controlled return flow "of a portion of :the stream being jpumped from the outlet side 'of the :pump .Past the hearing, 'as through the space between 'theshaft and the bearing means, into the shaft inlet, to :prevent excessive leakage from the high pressure outlet-to 'the 110w pressure inlet, and to llubricate and cool the bealring.

Another object is to provide, in a. jet operated turbine, a wheel housing having a peripheralcut-out for exposing successive segment-like portions of the wheel to ine jet at one side and exteriorly of the housing, and aguard means closing the cut-out, except for substantially minimum clearance for the wheel, whereby to :prevenvdanrage to the wheel and to the housing from the jet.

Another object is to provide a turbine of -the type indi t cated with means for controlling its power output, as

by providingfor relative movement between t h'e housing and the et for adjusting the wheel relative to the 'et Another object is to provide =purnp :means with port means coaxial with the axis o'f alpump, or other, rotor, as in the example given, where'in two :putnp rbtors ofa unit rotor having a driving turbine rotor therebetween, eagh has sueh port meansfor a fluid-different from the Qt er.

Another object is" to provide apparatus of "the "character indicated which is simple and durable in construction, economical to manufacture, and effective in its operation;

The above/and o'ther objects and ffeatures of the i'nvem tionwill appear more fully hereinafter from a consideration of the following descriptiontakcn in connection with the accompanying drawings wherein several embo diments of :portions of the invention are illustrated by way' of example.

"In the drawings:

(Figure 21 :is a side view partially in -seetion a'nd gpar tially in elevation lot a device constructed in accordance with the invention;

Figure 2-is a detail race view, as seen from the righ t,

of anrelement shown in :section toward -the deft-center of Figure 1;

Figure 3 is a blade section taken "along the-line G -B of Figure 1; t Figure 4 is an end view ofthe structure of Figure l, as viewed from the :right;

Figure 5 is a view "similar to a portion of Figure 4, as viewed from the left 'of :Figure 1;

Figure 6 is a,-group of tfigures including top edge and face views and a side :section normal to the :face' of a:

modified turbine blade of the invention;

Figure 7 is a group of :figures similairto Figure '6 of another modified blade;

l l'iiigure -8 is a group similar to .Figure 6 of another b a c;

Figure 9 is a group similar "to .Figure 6 of another blade;

Figure 10 is a group similar to Figure6 of atfurthen blade; -.and

Figure 11 is a typical force and velocity diagram. Referring, to Figures '1t, -4 andIS, the form oflthe invention therein shown by way of example only, comprisesa ptunp rotors 28and 30 and a turbine wheel 32-the axis of which, :in this instance, asshown, is substantiallytparallel to the jet from the nozzle 24. Fhe turbinenrotor or wheel 32 comprises ani-imperforateone-pieceelernent or disco-like body 34 andlincluding oppositely projecting:

hub portions 36 and 38, and blades 40 on the body or disc 34 wider than the thickness of the d1sc and short compared to the disc diameter, and adapted to extend only partially into the jet from one side, as indicated.

The blades 40 are designed and constructed in the form of airfoils to the end that the aerodynamic reaction of the jet flowing over the surfaces thereof produces a lift force that is utilized in driving or rotating the turbine wheel 32.

Since, as hereinbefore set forth, the velocity of the et of a jet propelled vehicle is in excess of the velocity of sound, in the instant illustration of the invention, each blade 40 has a supersonic airfoil section S, Figure 3, convergingly tapered outwardly from the disc 34 to an outer-end chisel edge 42 and, within its ability to effectively withstand the working stresses of its rated load, approaches the character of an infinitely thln flat plate having an angle of incidence B, Figure 11, relative to the turbine wheel axis CI, to provide an angle of attack A at which the rotor 32 is actuated at a given torque with substantially minimum reaction against the jet and hence minimum drag on the vehicle.

In the diagram of Figure 11, which illustrates the latter condition:

Cr=relative velocity Cl=jet velocity U=blade velocity B=angle of incidence A=angle of attack L=lift of blade D=drag of blade parallel to Cr R=resultant force on blade Bd=drag of blade (net loss) T=tangential force or useful torque A housing 44, enclosing the unit 20, comprises complementary substantially half portions or end members 46 and 48 of substantially cup-section secured to each other, as by a bolt 50, extending through each of a plurality of peripherally spaced pairs of mouth-end portions 52 and 54, respectively, engaged to each other. Margins 53 and 55 extending laterally of the cup sides 56 and 58, respectively, form radial cooling apertures in the housing for and opposite the blades 40 between each pair of portions 52 and 54, and closely conform to the sides 60 of the blades 40 about the wheel 32, except for axially registering peripheral cut-outs 62 and 64 for the passage along the wheel axis, between the blades 40, of a portion of the fluid jet exteriorly of the housing 44.

A centrifugal pump 66, having a casing portion 68 projecting from the bottom 70 of the cup 56, forms a chamber or outlet side 72 having an outlet 74, Figure 5, tangential to the side of the cup. Sealing means 76 is provided in the casing portion 68 between the latter and the hub portion 36.

A closure or plug 78 provided, at the bottom of the cup 56, for the other end of the casing 68, and having a screw threaded nipple portion 79 for attachment to a yieldable conduit, contains bearing means 80 for the hollow pump rotor 28, which is connected, as by a screw 84, to the adjacent or corresponding hub portion 36, against a washer 85, for driving by the rotor or wheel 32. The rotor 28 cooperates with a bore 82 of the closure plug 78 to form an inlet 86 coaxial with the wheel 32.

Means 88, providing for the cooling, sealing and lubrication of the bearing means 80, includes a Washer-like member 90, Figures land 2, having radial grooves 92. The means 88 provides for the controlled flow of fluid indicated by arrows Z in Figure 1, from the outlet side 72 of the pump 66 through a clearance M past the bearing 80, between the latter and a cover ring 94 on the hub .95 of the rotor 28. From the clearance M, the fluid enters the grooves 92, and passes to the inlet side of the rotor 28. The flow Z, which thus lubricates both the axial and thrust bearing surfaces, is reduced in pressure in the clearance M, and has small section area relative to the area of the low pressure inlet side of the pump.

A centrifugal pump 98, having a casing portion 100 projecting from the bottom 102 of the cup 58, forms a chamber or outlet side 104 having an outlet 106, Figure 4, tangential to the side of the cup.

The sizes and capacities of the pumps 66 and 98 are determined by thecharacter and quantity of the respective fluids delivered thereby. Sealing means 108, corresponding to the sealing means 76, and which, aside from being effective in its place, is not germane to this invention, is provided in the casing portion between the latter and the hub portion 38.

A closure or plug 110, provided at the bottom of the cup 58, for the other end of the casing 100, and having a nipple portion 111, contains bearing means 112 for the hollow pump rotor 30, which is connected, as by a screw 96 to the hub portion 38, against a washer 97, for driving by the wheel 32. The rotor 30 cooperates with a bore 114 of the closure plug to form an inlet 118 coaxial with the wheel 32.

Means 120, similar to the means 88, for providing for the cooling, sealing and lubrication of the bearing 112 includes another washer-like member 90 having radial grooves 92. The means 120 provides for the controlled flow of fluid, indicated by arrows Y, past the bearing 112, through a clearance N, from the outlet side 104 to the inlet side 118 of the pump rotor 30, as above set forth.

Each pump 66 and 98 is driven by the wheel 32 to pump a fluid different from the fluid pumped by the other.

Guards 130, as of stainless sheet steel, on the members 46 and 48, respectively, of the housing 44, close the cut outs 62 and 64, except for substantially minimum clearance for the wheel 32, it being of note that guard portions 132 are disposed in close running clearance relation of the disc 34 within the overhang or axial limits of the blades relative to the disc.

Means 134, including a bracket 136, a pivot pin 138 and an operating arm 140, provide for relative movement between the housing 44 and the jet from the nozzle 24 for adjusting the wheel 32 relative to the jet in either direction about the axis of the pin 138, Figure 1, from the mid position shown for varying the pressure of the fluid delivered by the pumps 66 and 98. Moving the wheel clockwise, through the angle Wi, fromthe position of Figure l, shifts the wheel further inwardly of the jet, and moving the wheel counterclockwise, through an equal angle W0, shifts the wheel outwardly of the jet.

In Figures 6-l0 modified blades A40, B40, C40, D40 and E40 have supersonic sections AS, BS, CS, DS and ES, respectively, indicating that a wide variety of shapes are possible.

Although several forms of the invention have been illustrated and described, various changes in the form and relative arrangements of the parts may be made to suit requirements.

What is claimed is:

l. The combination of a turbine wheel comprising an imperforate one-piece disc-like body including oppositely projecting hub portions, blades on the body wider than the thickness of the disc and short compared to the disc radius, a housing comprising end members of substantially cup-section secured with peripherally spaced month end attaching portions connected together across the wheel and portions extending laterally of the cup sides for the blades closely conforming to the blade sides about the wheel except for axially registering peripheral cut outs for the passage between the blades of a portion of a fluid jet exteriorly of the housing, a pump having a casing portion projecting from the bottom of each cup therein and forming a chamber having an outlet tangential to the side of the cup, sealing means between said casing portion and one of the hub portions, a closure at the bottom of the cup for the other end of the casing, bearing means in the closure, a hollow pump rotor connected to the corresponding hub portion for driving by the wheel and journaled in said closure bearing means and cooperating with the closure to form an inlet coaxial with the wheel, means for effecting cooling, sealing and lubrication of the bearing means including means providing for the controlled flow of fluid past the bearing from the outlet to the inlet side of the rotor, each pump being driven by the wheel to pump a fluid different from the fluid pumped by the other, guards on the housing closing said cut-outs except for substantially minimum clearance for the wheel, and operator-operative means providing for relative movement between the housing and the jet for adjusting the wheel relative to the jet.

2. In apparatus adapted 'to be driven by exhaust gases from an engine of a jet propelled vehicle; the combination comprising, a rotatable unit including a turbine wheel, a pump rotor at each side of the wheel, and a tubular shaft portion at each end of the unit effective as a pump inlet; bearing means for each hollow shaft por tion, the wheel including a body and blades, each blade having a supersonic airfoil section and, within its ability to effectively withstand the working stresses of its rated load, approaching the character of an infinitely thin fiat plate having an angle of incidence relative to the turbine wheel axis to provide an angle of attack at which the wheel is actuated at a given torque with substantially minimum reaction against the jet of exhaust gases and hence minimum drag on the vehicle, and means providing for the controlled return flow of fluid from the outlet side of each pump past the bearing means to the inlet side of the pump.

3. In apparatus adapted to be driven by exhaust gases from an engine of a jet propelled vehicle; the combination comprising a turbine wheel, a jet nozzle, a wheel housing having a peripheral cut out for exposing successive segment-like portions of the wheel to the jet, said jet nozzle being positioned at one side of the housing exteriorly of the housing, means pivotally mountingthe housing relative to the jet nozzle and providing for relative movement between the housing and the jet, and operator-operative means for adjusting the wheel housing relative to the jet.

Babbitt Sept. 30, 1879 Keller Nov. 14, 1905 893,217 Wyand July 14, 1908 1,013,317 Samuelson July 2, 1912 1,333,987 McManigal Mar. 16, 1920 1,704,691 Carpenter Mar. 12, 1929 1,812,741 Espinosa June 30, 1931 2,083,167 Lamere June 8, 1937 2,199,243 Mortimer Apr. 30, 1940 2,209,109 Bungartz July 23, 1940 --2,258,793 New Oct. 14, 1941 2,258,794 Way Oct. 14, 1941 2,364,189 Buchi Dec. 5, 1944 2,419,689 McClintock Apr. 29, 1947 2,435,236 Redding Feb. 3, 1948 2,450,950 Goddard Oct. 12, 1948 2,465,930 Robinson Mar. 29, 1949 2,479,039 Cronstedt Aug. 16, 1949 2,487,532 Eastman Nov. 8', 1949 2,591,549 Jonker Apr. 1, 1952 2,611,532 Ljungstrom Sept. 23, 1952 2,616,373 Goddard Nov. 4, 1952 2,623,357 Birmann Dec. 30, 1952 FOREIGN PATENTS 302,924 Germany Apr. 15, 1917 318,376 Germany Jan. 26, 1920 OTHER REFERENCES N. A. C. A. Technical Note No. 1211. The Flow and Force Characteristics of Supersonic Airfoils at High Subsonic Speeds, March 1947. 

